Panel-Mounted Aircraft Control Stick

ABSTRACT

A panel-mounted control stick for aircraft providing for roll and pitch input that emulates the response of a traditional floor-mounted control stick. The panel-mounted control stick incorporates a pitch beam input assembly and a roll input assembly for translating the movements of the control stick into movements of aircraft control surfaces.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a continuation-in-part of U.S. patent applicationSer. No. 12/163,388 filed on Jun. 27, 2008, the disclosure of which isincorporated herein by reference.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The invention relates generally to aircraft. More specifically, theinvention relates to the field of control systems design.

2. Description of the Related Art

Traditional, floor-mounted control sticks for input of pitch and rollmovements to an aircraft have long been known in the aviation arts. Suchcontrol sticks have significant drawbacks. These sticks make itdifficult for pilots to get into and out of the cockpit because thestick blocks access to the floor of the cockpit, and the pilot mustclimb over it to get into the pilot's seat. Side-mounted sticks provideeasier access than a traditional control stick, but may only be operatedwith one hand and lack the mechanical advantage of the center mountedstick. An alternative panel-mounted yoke also provides easier access,but may cause safety issues due to a limited range of motion due toobstruction of the yoke by the pilot's legs. The panel-mounted stickdisclosed in this application addresses these, and other, issues inaircraft control systems.

SUMMARY

The invention is defined by the claims below. Embodiments of theinvention include a panel-mounted control stick for controlling thepitch and roll of an aircraft. The system includes a pitch beam assemblyand a control stick assembly. The pitch beam assembly includes a pitchbeam and a pitch beam input assembly. The pitch beam assembly, inembodiments, includes a control stick bracket, a pitch beam bracket, anda swivel assembly. The roll input assembly, in embodiments, includes twobellcranks, two spool bearings, and a shaft retainer.

BRIEF DESCRIPTION OF THE DRAWINGS

Illustrative embodiments of the present invention are described indetail below with reference to the attached drawing figures, which areincorporated by reference herein:

FIG. 1 is a perspective view of an aircraft incorporating an embodimentof the panel-mounted control stick;

FIG. 2 is a perspective view of an embodiment of the panel-mountedcontrol stick;

FIG. 3 is a side view of an embodiment of the panel-mounted controlstick;

FIG. 4 is a detailed side view of an embodiment of the pitch beam inputassembly;

FIG. 5 is a cross-sectional view of an embodiment of the pitch beaminput assembly;

FIG. 6 is a top view of an embodiment of the panel-mounted controlstick;

FIG. 7 is a conceptual view of a traditional aircraft control stick;

FIG. 8 is an end view of an embodiment of the panel-mounted controlstick;

FIG. 9 is detailed top view of an embodiment of the roll input assembly;

FIG. 10 is a cross-sectional view of an embodiment of the roll inputassembly.

FIG. 11 is a detailed top view of an embodiment of the roll inputassembly; and.

FIG. 12 is a cross-sectional view of an embodiment of the roll inputassembly.

DETAILED DESCRIPTION

Referring now to FIG. 1, an aircraft 100 contains an embodiment ofcontrol stick module 102 located in the cockpit area of aircraft 100.Aircraft 100 shown in FIG. 1 is a small aircraft commonly known inaviation; however the panel-mounted control stick could be utilized innumerous other sorts of aircraft and other aircraft designs instead ofthat shown in FIG. 1. Aircraft 100 includes various control surfaces,including an aileron pair 104 for controlling the roll of aircraft 100and an elevator pair 106 for controlling the pitch of aircraft 100. Thespecific control surfaces shown on aircraft 100 may also compriseelevons or various other designs for aircraft control surfaces. Thespecific design for aircraft 100 shown in FIG. 1 does not form any partof the invention but is merely for illustrative purposes.

Control stick module 102 comprises at least one control stick assembly108 and pitch beam assembly 110, which will be described in furtherdetail below. FIG. 1 displays an embodiment of the invention comprisingtwo control stick assemblies 108. In other embodiments of the inventionthere may be only one control stick assembly or the control stickassemblies may be located in different relative configurations.

The control stick assemblies 108 are connected through various linkagesto the control surfaces of aircraft 100 to allow for movement thereof ina manner known to those skilled in the art. Thus, pitch and roll areable to be controlled by the pilot of aircraft 100 in flight bymanipulating stick assemblies 108. A pilot and optional co-pilot inputpitch and roll control to the aircraft 100 by various movements ofcontrol stick assemblies 108.

The user inputs necessary for operation of control stick module 102 by apilot are similar to those of traditional aircraft control sticks knownin the aviation arts. Pushing forward on the control stick assembly 108causes the control surfaces to move and pitch the nose of aircraft 100down, while pulling back on control stick assembly 108 causes the noseof aircraft 100 to pitch up. Similarly, pushing right on control stickassembly 108 moves the control surfaces causing aircraft 100 to rollright, and pushing left on the control stick assembly 108 causesaircraft 100 to roll left.

Referring now to FIG. 2, a detailed perspective view of an embodiment ofthe control stick assembly 108 and the pitch beam assembly 110 is shown.Pitch beam assembly 110 comprises a pitch beam 200 and one or more pitchbeam input assemblies 202. Each pitch beam input assembly 202 translatesmovement of one control stick assembly 108 into movement of pitch beam200 and thus to the appropriate control surfaces, such as elevator 106through various linkages of types commonly known in the aviation arts.

The control stick assembly 108 comprises control stick shaft/inputtranslating member 204, control stick grip/input receiving member 206and roll input assembly/first attitudinal control member 208. Controlstick grip 206 is utilized by the pilot of aircraft 100 for manual inputof roll and pitch control movements, and may be formed of metal, plasticor a combination thereof. Control stick grip 206 incorporates a socketfor receiving a first end of control stick shaft 204, and is alsosecured to shaft 204 by bolts, screws or other similar means ofattachment. Grip 206, in the FIG. 2 embodiment, is substantiallyperpendicular to control stick shaft 204, though it may be inclinedslightly forward for comfort of the pilot. Control stick shaft 204 isformed from circular metal tube, though solid bar or shafts with othercross-sectional shapes may be utilized. A second end of control shaft204 is connected to pitch beam 200 by pitch beam input assembly 202.

Pitch beam input assembly 202 comprises a control stick bracket/firstrotational translation member 210, a swivel assembly/multi-directionalconnecting member 212, and pitch beam brackets/second rotationaltranslation member 214. Brackets 210 and 214 may be formed from bentmetal plate, or forged, cast or otherwise shaped as shown. Swivelassembly 212, in the disclosed embodiment, is machined or cast fromsolid metal. The control stick bracket 210 is attached to the second endof control stick shaft 204 by bolts or other appropriate means ofattachment including welding. Alternatively, control stick bracket 210may be formed as an integral part of control stick shaft 204 throughmachining, welding, casting or other similar means.

Swivel assembly 212 is rotatably attached to control stick bracket 210by control stick swivel bolt 216. The rotatable connection allowscontrol stick bracket 210 to rotate around the longitudinal axis of bolt216 thus allowing the side to side movement of control shaft 204necessary for the roll input.

Swivel assembly 212 is also rotatably attached to a first end of pitchbeam brackets 214 by pitch beam swivel bolt 218. The longitudinal axisof pitch beam swivel bolt 218 is substantially parallel to thefunctional axis of the pitch beam, as described below. The second endsof pitch beam brackets 214 are each attached by means of welding, boltsor other fixed attachment, to pitch beam 200, such that translation ofthe first end of pitch beam brackets 214 causes pitch beam 200 to rotateabout its functional axis.

During operation of the control stick module 102, fore and aft movementof control stick grip 206 is transmitted along control stick shaft 204to control stick bracket 210 and swivel assembly 212, which translatesthe first ends of pitch beam brackets 214. The translation of pitch beambracket 214 causes pitch beam 200 to rotate around its functional axis.The rotation of pitch beam 200 is transmitted to control surfaces, suchas elevator 106, by means of control linkages as known in the aviationarts, such as cables, rods, or wires.

The functional axis of pitch beam 200 may be varied according to themeans of mounting pitch beam 200, and may be coincident with thelongitudinal axis of pitch beam 200 or may be offset by means of anoffset mounting. The embodiment shown in FIG. 2 has an offset functionalaxis due to pitch beam mounting bracket 220. Bracket 220, in thedisclosed embodiments, is formed from metal plate cut to the requiredshape and attached to pitch beam 200 by welding. Pitch beam mountingbracket 220 is rotatably attached to the frame of aircraft 100 providingsupport for pitch beam assembly 110 as well as allowing pitch beam 200to rotate around its functional axis. Additional brackets 220 may beprovided as necessary to properly support pitch beam 200.

The roll input assembly 208 provides support to control stick shaft 204and accepts input of roll commands from the pilot of aircraft 100. Rollinput assembly 208 comprises two spool bearings 222, two bellcranks 224,two spool bearing mounting bolts 226 and two bellcrank mounting bolts228. Bellcranks 224, in the disclosed embodiments, are formed from castor machined metal.

Spool bearings 222 are formed from metal, or some other suitablematerial, and have a top, a bottom and an interior concave face. Theinterior face of the spool bearings 222 is concave in some embodiments.The spool bearings 222 have substantially circular cross-sectionsparallel to the top and bottom faces thereof, which is more clearlyshown in FIG. 9 described below. The cross-sections of spool bearings222 perpendicular to the top and bottom faces thereof vary based on thegeometry of the interior concave face. The concave face may have asubstantially semi-circular geometry, as shown in the embodiment shownin FIG. 10. The concave face may alternatively comprise two interiorplanar surfaces disposed at an angle to each other, one extending fromthe top surface of the spool bearing 222 and the other extending fromthe bottom surface of spool bearing 222, and intersecting at a pointsubstantially midway between the top and bottom surfaces of spoolbearing 222 and between the outer edge of the top and bottom surfacesand the bolts 226. The spool bearing 222 may also comprise multiplepieces, as shown in FIG. 12 below.

Each spool bearing 222 depends from and is rotatably attached to abellcrank 224 by spool bearing mounting bolt 226, which extends throughspool bearing 222 perpendicular to the top and bottom faces of thebearing 222. Each bellcrank 224 is rotatably attached to the frame ofaircraft 100 by a bellcrank mounting bolt 228. An additional embodimentof the spool bearings 222 and the roll input assembly is described anddiscussed below in relation to FIGS. 11 and 12.

Control linkages, as commonly known in the aviation arts, connect thebellcranks 224 to control surfaces, such as ailerons 104, on aircraft100. As shaft 204 is translated left or right by movement of grip 206,the shaft 204 exerts a force on the left or right spool bearing 222. Theforce is transmitted from spool bearing 222 to bellcrank 224, causingthe bellcranks 224 to rotate around bolt 228. As bellcranks 224 rotateleft or right around bolt 228 the control linkages transfer the movementto the control surfaces thus causing aircraft 100 to roll left or right.

Spool bearings 222 are positioned on opposing sides of shaft 204 and theconcave faces of spool bearings 222 support shaft 204 and allow it totranslate fore and aft as spool bearings 222 rotate around bolts 226.

Referring now to FIG. 3, a side view of an embodiment of the controlstick module 102 is shown. In this view it can be seen that the controlbracket 210 secures shaft 204 at an angle 300 to the surface of swivelassembly 212.

Control stick grip 206 is pushed fore and aft by the pilot of aircraft100 to pitch the nose of the aircraft down and up, respectively. Whengrip 206 is pushed forward to position 302 control stick shaft 204translates forward thus rotating pitch beam bracket 214 to fore position304. When grip 206 is pulled back to aft position 306 then shaft 204translates aft thus rotating pitch beam bracket 214 to aft position 308.

FIG. 4 provides a detailed side view of an embodiment of the pitch beaminput assembly 202. As can be seen more clearly here, angle 300 subtendsan arc between a first surface 400 of control stick bracket 210, and acentral axis 402 of shaft 204. Bolt 216, around which bracket 210swivels, is substantially perpendicular to the first surface 400. Theangle 404, between axis 402 and the axis of bolt 216, is equal to angle300 minus 90 degrees. The angle 300 may be varied in differentembodiments of the panel-mounted stick, and as is discussed in detailbelow, altering this angle varies the operation of the panel-mountedstick system.

FIG. 5 is a cross-sectional view of an embodiment of swivel assembly212, pitch beam bracket 214 and control stick bracket 210 along the lineI-I on FIG. 4. Bolt 216 rotatably attaches swivel assembly 212 tobracket 210. Bolt 216 is supported within swivel assembly 212 bybearings 500, which are formed from metal or some other suitablematerial. Metal washer 502, castellated nut 504 and cotter pin 506secure bracket 210 to swivel assembly 212. Bolt 218, not shown on FIG.4, similarly attaches bracket 214 to swivel assembly 212.

FIG. 6 is a top view of an embodiment of the control stick module 102showing the range of motion of the control stick assembly 108 and thepitch beam assembly 110. As the pilot of aircraft 100 moves the grip 206to the left and right, control shaft 204 presses against spool bearings222 causing bellcranks 224 to move left to position 600 and right toposition 602, respectively. Control linkages, commonly known in theaviation arts, connect bellcranks 224 to control surfaces of aircraft100 (e.g., ailerons 104 shown in FIG. 1) for causing the aircraft toroll. At any point of movement left and right between position 600 andposition 602, the grip 206 may also be moved fore and aft to actuate thepitch beam input assembly 202.

FIG. 7 is a representation of a traditional control stick as seen fromthe pilot's location in aircraft 100. A traditional control stick 700extends vertically from the cockpit floor 702, thus as it is moved leftor right the end of the control stick 700 follows an arc around thepivot point of the control stick 700. This causes the longitudinal axisof the grip 704 to tilt from side to side as the stick is translatedleft or right to positions 706 and 708. The angle of tilt is determinedby the extent of movement side to side and by the length 710 of thecontrol stick 700.

FIG. 8 is a view of an embodiment of the control stick module 102 fromthe pilot's location within the cockpit of aircraft 100. The controlstick module 102 emulates the traditional aircraft control stick shownin FIG. 7 in several respects, one of which is the tilt of the controlgrip 206 as it is translated to the left or right by the pilot ofaircraft 100. In the neutral position the longitudinal axis 800 of grip206 extends perpendicular to the floor of the cockpit of aircraft 100.When moved to the left to position 802 or to the right to position 804the longitudinal axis 800 of grip 206 tilts to the left or rightrespectively. The grip 206 tilts in the same manner as though it were ona traditional control stick extending to the floor of the cockpit.

The tilting of grip axis 800 is caused by the rotating of shaft 204 andbracket 210 around bolt 216. The angle 300, shown in FIG. 3, causes thefirst end of shaft 204 to describe an arc 806 when shaft 204 rotatesaround bolt 216. The grip 206 is attached in a fixed orientation to thefirst end of shaft 204 and thus remains substantially perpendicular fromthis perspective, to the tangent of the arc 806 described by shaft 204which causes the grip to tilt as it is moved from side to side. Thismovement of grip 206 is equivalent to the movement of grip 206 ifattached to the top of a virtual control stick extending to the cockpitfloor of aircraft 100. The apparent length of the virtual control stick,x, is:

x=y tan(angle 404) or equivalently x=y tan(angle 300−90 degrees);

where y is the length of control stick shaft 204.

FIG. 9 is a detailed top view of an embodiment of the roll inputassembly 208. Bellcrank mounting bolts 228 and spool bearing mountingbolts 226 are secured by castellated nuts 900 and cotter pins 902.Bellcranks 224 have various attachment points for linkages to controlsurfaces on aircraft 100, such as mounting point 904, mounting bracket906 and cable guard 908.

FIG. 10 is a cross-sectional view of an embodiment of spool bearings 222and bellcranks 224 along axis 910 shown in FIG. 9. Spool bearings 222and bellcranks 224 are secured on bolts 226 by washers 1000 and 1002,and castellated nut 900 and cotter pin 902. In this embodiment of theroll input assembly 208, bolts 226 are disposed with the head of eachbold 226 located generally below bellcrank 224 and with castellated nut900 located generally above bellcrank 224. In addition, the two bolts226 may be optionally connected by shaft retainer 1004. Retainer 1004allows bolts 226 to rotate freely in relationship to retainer 1004, butmaintains the fixed separation distance between bolts 226 thus securelyholds shaft 204 between spool bearings 222. The retainer 1004 and thefixed location of the bellcrank mountings by bolts 228 allow bellcranks224 to individually rotate about bolts 228 in response to roll inputreceived through shaft 204 while remaining substantially parallel toeach other and applying appropriate inputs to control linkages aspreviously described.

FIG. 11 is a detailed top view of another embodiment of the roll inputassembly 208. This embodiment of the roll input assembly includes thesame elements described in FIG. 10 above with a different spool bearingdesign. In this embodiment of the roll input assembly 208 bolts 226 aredisposed with the head of each bolt 226 generally located abovebellcrank 224, and castellated nuts 900 (see FIG. 12) generally locatedbelow bellcrank 224. It additionally includes a retaining clip 1104.Retaining clip 1104 operates in a similar fashion to retainer 1004 tomaintain bolts 226 at a fixed distance apart as bellcranks 224 rotatearound bolts 228. Retaining clip 1104 is pivotally secured on the topsurface of bellcranks 224 and held in place by bolts 226. Alternatively,retaining clip 1104 could be positioned between bellcranks 224 and spoolbearings 222.

FIG. 12 is a cross-sectional view of another embodiment of spoolbearings 222 and roll input assembly 208 along axis 1106 shown in FIG.11. Retaining clip 1104 is shown rotatably attached at each end to bolts226 between a top surface 1201 of each bellcrank 224 and the head ofbolt 226 or castellated nut 900, depending on the orientation of bolt226. Retaining clip 1104 is separated from each bolt 226 by bushing 1202which extends along bolt 226 a distance slightly more than the width ofretaining clip 1104. Washers 1204 separate bushing 1202 from the head ofbolt 226 (or alternatively from nut 900) and from top surface 1201 ofbellcrank 224. This allows castellated nut 900 to be tightened on bolt226 without binding clip 1104 and preventing clip 1104 from rotatingaround bolts 226. One or more washers 1204 may be stacked as necessary,wherever washers 1204 are in use, to adjust for the length of bolt 226,the dimensions of bellcrank 224 and the adjustment of spool bearings222.

Clip 1004, described in relation to FIG. 10 above, is also separatedfrom bolts 226 by bushing 1206 and washers 1208. This similarly preventsclip 1004 from binding against nut 900 or bolt 226 when tightened.Washers 1208 also separate spool bearings 222 from bellcranks 224 andfrom nut 900 (or alternatively from the head of bolt 226) to allow forrotation of the spool bearings around bolt 226.

FIG. 12 also shows an alternative embodiment of spool bearings 222comprising a two part spool bearing 222. In this embodiment of the spoolbearings 222, each spool bearing comprises a top bearing 1210 and abottom bearing 1212. Both top and bottom bearings are frusto-conical inshape, with a cylindrical hole through the axis of the cone to receivebolt 226. The top bearing 1210 has a large circular surface (or base)1214, a small circular surface (or tip) 1216 and a conical surface 1218.The bottom bearing 1212 has a large circular surface (or base) 1220, asmall circular surface (or tip) 1222 and a conical surface 1224. The topbearing 1210 and the bottom bearing 1212 of each spool bearing 222 arepositioned relative to each other so that the small surface 1216 of topbearing 1210 is disposed substantially parallel to the small surface1222 of bottom bearing 1212, and separated therefrom by a shortdistance. Bolt 226 passes through the cylindrical hole through theconical axis of the top bearing 1210 and bottom bearing 1212,maintaining their linear alignment. Control stick 204 is held againstthe conical surfaces 1218 and 1224 of the two spool bearings 222 on thetwo bolts 226, which are maintained the required distance apart byretaining clips 1004 and 1104. The conical surfaces 1218 and 1224provide support to the control stick 204, while allowing it, throughrotation of the spool bearings 222, to move fore and aft to provideinput to the pitch beam input assembly. The spool bearings also allowthe pilot to control the roll of the aircraft by translating theside-to-side movement of control stick 104 to bellcranks 224 and thusthrough control linkages, to the control surfaces of the aircraft.

The distance between surfaces 1222 and 1216 is determined by the numberof washers 1208, which may be varied to adjust the distance betweensurfaces 1222 and 1216 to an optimal distance. The optimal distancebetween the surfaces depends on the circumference of control stick shaft204 and the optimal friction between shaft 204 and spool bearings 222when moving the shaft to provide control input to the aircraft.

1. A panel-mounted control stick module for controlling an aircraftcomprising; at least one control stick assembly for receiving an inputfrom a user; and a pitch beam assembly, said control stick assembly,upon receiving said input, rotating said pitch beam assembly for thepurpose of translating a first control surface of the aircraft.
 2. Thepanel-mounted control stick of claim 1 wherein, the control stickassembly, upon receiving a second input, translates a second controlsurface of the aircraft.
 3. The panel-mounted control stick of claim 2wherein the at least one control stick assembly comprises: a controlstick grip; a control stick shaft; and a roll input assembly; whereinthe control stick grip is mounted on a first end of the control stickshaft and is substantially perpendicular to the control stick shaft;wherein the roll input assembly is rotatably attached to the frame ofthe aircraft; and wherein the control stick shaft is supported by theroll input assembly.
 4. The panel-mounted control stick of claim 3wherein the roll input assembly comprises: a first bellcrank and asecond bellcrank, wherein each bellcrank is rotatably attached to theframe of the aircraft at a first end of each bellcrank; a first spoolbearing and a second spool bearing; a first spool bearing bolt and asecond spool bearing bolt; a shaft retainer; wherein the first spoolbearing depends from and is rotatably attached to a second end of thefirst bellcrank by the first spool bearing bolt; wherein the secondspool bearing depends from and is rotatably attached to a second end ofthe second bellcrank by the second spool bearing bolt; wherein thecontrol stick shaft is maintained between the first spool bearing andthe second spool bearing with longitudinal and pivotal freedom ofmovement; wherein the first spool bearing bolt and the second spoolbearing bolt are rotatably maintained adjacent to and in support of thecontrol stick shaft by the shaft retainer; wherein transversetranslation of the control stick shaft translates the first and secondspool bearing and the first and second bellcrank for the purpose oftranslating the control surfaces of the aircraft.
 5. The panel-mountedcontrol stick of claim 4 wherein the first and second spool bearing eachcomprise: a top bearing and a bottom bearing; wherein the top bearingand the bottom bearing are frusto-conical in shape and include acylindrical hole along the conical axis thereof to receive the spoolbearing bolt.
 6. The panel-mounted control stick of claim 5 wherein thebottom bearings and the top bearings each have a conical surface, a baseand a tip; and wherein the bottom bearing and the top bearing dependfrom the spool bearing bolt with the tip of the top bearingsubstantially parallel and slightly removed from the tip of the bottombearing; and wherein the control stick shaft is maintained between theconical surfaces of the top and bottom bearings.
 7. The panel-mountedcontrol stick of claim 3, wherein the pitch beam assembly comprises: apitch beam shaft; a pitch beam input assembly; wherein the pitch beamshaft is rotatably attached to the frame of the aircraft around an axisof rotation; wherein the pitch beam input assembly connects the controlstick shaft to the pitch beam shaft; and wherein longitudinal movementof the control stick shaft rotates the pitch beam input assembly and thepitch beam around the axis of rotation.
 8. The panel-mounted stick ofclaim 7, wherein the pitch beam input assembly comprises: a controlshaft bracket fixedly attached to a second end of the control shaft; afirst pitch beam bracket and second pitch beam bracket, wherein bothpitch beam brackets are fixedly attached to the pitch beam at a firstend of each pitch beam bracket; a swivel assembly rotatably attachedbetween the second end of the pitch beam brackets wherein the axis ofrotation of the swivel assembly with the pitch beam brackets issubstantially parallel to the axis of rotation of the pitch beam; andwherein the swivel assembly is rotatably attached to the control stickbracket by a control stick swivel bolt whose longitudinal axis issubstantially perpendicular to the longitudinal axis of the pitch beamswivel bolt, and further whose longitudinal axis is substantiallyperpendicular to the control stick bracket; wherein longitudinaltranslation of the control stick bracket rotationally translates thepitch beam for the purpose of translating the control surfaces of theaircraft.
 9. A control system comprising: an input receiving member forreceiving input from a user of the control system; a input translatingmember for translating the input received by the input receiving memberto a first attitudinal control member for controlling the attitude of anaircraft in a first dimension and a first rotational translation memberfor controlling the attitude of the aircraft in a second dimension;wherein the first rotational translation member is rotatably attached toa multi-directional connecting member for communicating; wherein themulti-directional connecting member is rotatably attached to a secondrotational translation member; and wherein the second rotationaltranslation member translates a second attitudinal control member. 10.The control system of claim 9 wherein the input translating membertranslates the first attitudinal control member in a plane oftranslation that is substantially perpendicular to the plane oftranslation of the first rotational translation member.
 11. The controlsystem of claim 9 wherein the rotatable attachment of the firstrotational translation member to the multi-directional connecting memberis substantially perpendicular to rotatable attachment of themulti-directional connecting member to the second rotational translationmember.
 12. A panel mounted control stick for controlling the attitudeof an aircraft comprising: a control stick grip for receiving input froma pilot of the aircraft, containing a socket for receiving a first endof the control stick shaft; said control stick shaft being supported ata point substantially at its midpoint between a first and second spoolbearings; said first and second spool bearings depending from androtatably attached to a first and second bellcrank, respectively; saidfirst and second bellcrank being rotatably attached to the frame of theaircraft and to control surfaces of the aircraft; said control stickshaft being connected at a second end to a control stick bracket; saidcontrol stick bracket being rotatably connected to a swivel assembly;said swivel assembly being rotatably connected to a pitch beam bracket;said pitch beam bracket being attached to a pitch beam and to controlsurfaces of the aircraft; wherein transverse translation of the controlstick shaft translates the first and second spool bearings and the firstand second bellcranks, for translating the control surfaces of theaircraft; and wherein longitudinal translation of the control stickshaft translates the pitch beam, for translating the control surfaces ofthe aircraft.